EP1733134A2 - Inverseur de poussee mis en service par une suspension en forme d'araignee - Google Patents

Inverseur de poussee mis en service par une suspension en forme d'araignee

Info

Publication number
EP1733134A2
EP1733134A2 EP04821621A EP04821621A EP1733134A2 EP 1733134 A2 EP1733134 A2 EP 1733134A2 EP 04821621 A EP04821621 A EP 04821621A EP 04821621 A EP04821621 A EP 04821621A EP 1733134 A2 EP1733134 A2 EP 1733134A2
Authority
EP
European Patent Office
Prior art keywords
yoke
rods
drive
doors
reverser
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP04821621A
Other languages
German (de)
English (en)
Other versions
EP1733134A4 (fr
Inventor
Jean-Pierre Lair
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Nordam Group LLC
Original Assignee
Nordam Group LLC
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Nordam Group LLC filed Critical Nordam Group LLC
Publication of EP1733134A2 publication Critical patent/EP1733134A2/fr
Publication of EP1733134A4 publication Critical patent/EP1733134A4/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/76—Control or regulation of thrust reversers
    • F02K1/763—Control or regulation of thrust reversers with actuating systems or actuating devices; Arrangement of actuators for thrust reversers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • a typical turbofan aircraft engine includes a fan powered by a core engine for producing propulsion thrust for powering the aircraft in flight.
  • the core engine typically has in serial flow communication a multistage axial compressor, annular combustor, and high pressure turbine joined to the compressor by one shaft.
  • a second shaft joins the fan to a low pressure turbine disposed downstream from the high pressure turbine.
  • the engine also includes a fan nacelle surrounding the cowling or nacelle of the core engine which defines an annular bypass duct therebetween.
  • the nacelle may be short and terminates in a fan outlet nozzle surrounding the core engine upstream from an independent core exhaust nozzle at the downstream end thereof. Or, the fan nacelle may be long and extends downstream past the core nozzle for collectively discharging both the fan bypass air and the core exhaust in a common exhaust nozzle disposed downstream therefrom.
  • the turbofan engine typically also includes a fan thrust reverser for providing aerodynamic braking during aircraft landing on a runway.
  • Various types of fan thrust reversers are known in the art, one of which includes pivoting doors that block the aft travel of the fan air in .the bypass duct and redirect it in the forward direction for reversing the direction of fan air thrust.
  • the known fan reversers have various advantages and various disadvantages relating to complexity, size, weight, and cost.
  • the pivoting door fan reverser requires multiple sets of deployment actuators and linkage.
  • the use of multiple actuators correspondingly increases the complexity, weight, and cost of the reverser system and its control.
  • U.S. Patent Application No. 10/679,882; filed 10/06/2003, and assigned to the present assignee discloses an improved bifold door thrust reverser having many advantages over typical fan thrust reversers.
  • the bifold door reverser includes outer and inner doors which are deployed in opposition for blocking and turning the fan bypass flow during thrust reverse operation.
  • a gang of the outer doors may be deployed in unison with a common inner door, all deployed using a common actuator.
  • the outer and inner doors maintain continuity of the outer and inner skins of the nacelle when stowed, and the actuation mechanism is fully contained in the nacelle between the two skins.
  • the bifold door reverser is relatively compact and requires relatively small stroke of the multiple actuators used therein. However, the multiple actuators and control system therefor correspondingly increases weight, cost, and complexity. Accordingly, it is desired to further improve the bifold door thrust reverser by reducing the number of actuators required for deployment thereof.
  • a thrust reverser includes reverser doors circumferentially spaced around a nacelle.
  • An arcuate yoke is disposed coaxially around the nacelle.
  • An actuator is mounted tangentially to the yoke for rotary movement thereof.
  • Actuator rods join the doors to the yoke for simultaneous deployment of the doors as the yoke is rotated.
  • Figure 1 is a partly sectional axial view of an exemplary turbofan aircraft gas turbine engine mounted to an aircraft wing, and including a fan thrust reverser integrated in the fan nacelle thereof.
  • Figure 2 is an axial sectional view of the fan reverser illustrated in Figure 1 shown in a stowed position.
  • Figure 3 is an axial sectional view of the fan reverser illustrated in Figure 2 shown in a deployed position.
  • Figure 4 is an enlarged isometric view of a representative set of the reverser doors illustrated in Figure 1 in an exemplary embodiment.
  • Figure 5 is an isometric view of the actuation system illustrated in Figures 2 and 3 shown in isolation from the reverser doors.
  • Figure 6 is an enlarged isometric view of the actuator for driving the yoke illustrated in Figure 5.
  • Figure 7 is a partly sectional, isometric view of an exemplary portion of the actuation system illustrated in Figure 2 with extended rod for stowing closed the reverser doors as illustrated in Figure 2.
  • Figure 8 is a partly sectional, axial view, like Figure 7, of the actuation system including the retracted rod for deploying open the reverser doors as illustrated in Figure 3.
  • Figure 9 is a top, partly sectional view of the actuation system illustrated in Figures 7 and 8 with the rod being disposed at an intermediate axial position between extended and retracted.
  • FIG. 1 Illustrated in Figure 1 is a turbofan aircraft gas turbine engine 10 suitably mounted to the wing 12 of an aircraft by a supporting pylon 14. Alternatively, the engine could be mounted to the fuselage of the aircraft if desired.
  • the engine includes an annular fan nacelle 16 surrounding a fan 18 which is powered by a core engine surrounded by a core nacelle or cowl 20.
  • the core engine includes in serial flow communication a multistage axial compressor 22, an annular combustor 24, a high pressure turbine 26, and a low pressure turbine 28 which are axisymmetrical about a longitudinal or axial centerline axis 30.
  • ambient air 32 enters the fan nacelle and flows past the fan blades into the compressor 22 for pressurization.
  • the compressed air is mixed with fuel in the combustor 24 for generating hot combustion gases 34 which are discharged through the high and low pressure turbine 26,28 in turn.
  • the turbines extract energy from the combustion gases and power the compressor 22 and fan 18, respectively.
  • a majority of the air is pressurized by the driven fan 18 for producing a substantial portion of the propulsion thrust powering the aircraft in flight.
  • the combustion gases 34 are exhausted from the aft outlet of the core engine for providing additional thrust.
  • thrust reversal is desired for aerodynamically slowing or braking the speed of the aircraft as it decelerates along a runway.
  • the turbofan engine 10 includes a fan thrust reverser 36 wholly contained in or integrated into the fan nacelle 16 for selectively reversing fan thrust during aircraft landing.
  • the fan thrust reverser, or simply fan reverser 36 is integrated directly into the fan nacelle 16.
  • the fan nacelle includes radially outer and inner cowlings or skins 38,40 which extend axially from a leading edge of the nacelle defining an annular inlet 42 to an opposite trailing edge defining an annular outlet 44.
  • the fan nacelle 16 may have any conventional configuration, and is typically formed in two generally C-shaped halves which are pivotally joined to the supporting pylon 14 for being opened during maintenance operations.
  • the exemplary fan nacelle illustrated in Figure 1 is a short nacelle terminating near the middle of the core engine for discharging the pressurized fan airflow separately from and surrounding the exhaust flow 34 discharged from the aft outlet of the core engine.
  • the fan nacelle could be long and extend downstream of the core engine for providing a single, common outlet for both the fan air and the core exhaust.
  • the core engine is mounted concentrically inside the fan nacelle 16 by a row of supporting struts in a conventional manner.
  • the core cowl 20 is spaced radially inwardly from the inner skin 40 of the fan nacelle to define an annular bypass duct 46 therebetween which bypasses a major portion of the fan air around the core engine during operation.
  • the fan bypass duct terminates in an annular fan nozzle 48 at the nacelle trailing edge or outlet 44.
  • a particular advantage of the fan reverser 36 is that the fan nozzle 48 itself may remain fixed at the aft end of the fan nacelle surrounding the core engine. And, the fan reverser 36 may be fully integrated in the fan nacelle immediately forward or upstream from the fixed fan nozzle.
  • the fan reverser is illustrated in more detail in Figures 2 and 3 wherein the outer and inner skins 38,40 are spaced radially apart to define an arcuate compartment or annulus 50 spaced axially forwardly from the nacelle trailing edge 44.
  • the nacelle compartment 50 includes a flow tunnel or aperture 52 extending radially between the inner and outer skins through which the pressurized fan bypass air 32 may be discharged during thrust reverse operation.
  • At least one, and preferably a gang or set of radially outer louver doors 54,56 are suitably pivotally joined to the fan nacelle in the compartment 50 to close the exit end of the tunnel along the outer skin 38. Two or more of the louver doors may be axially nested together as further described hereinbelow.
  • a corresponding radially inner reverser or blocker door 58 is suitably pivotally joined to the fan nacelle 16 inside the compartment 50 in radial opposition with the gang of louver doors to close the inlet end of the tunnel along the inner skin 40.
  • the inner door In the stowed closed position illustrated in Figure 2, the inner door is folded closed generally parallel with the corresponding gang of outer doors, converging slightly to conform with the converging profile or cross section of the nacelle.
  • the fan bypass duct 46 illustrated in Figures 1-3 is substantially annular, the fan reverser includes corresponding groups of the louver doors 54,56 and cooperating blocker door 58 spaced circumferentially apart around the perimeter of the fan nacelle 16.
  • each half C-duct portion of the fan nacelle three groups of the blocker and louver doors are uniformly spaced apart from each other.
  • An elongate drive link 60 pivotally joins together the outer and inner doors for coordinating the simultaneous deployment thereof.
  • a spider actuation mechanism or system 62 is suitably mounted in the nacelle compartment and joined to the doors for selective rotation thereof from the stowed position illustrated in Figure 2 at which the doors are pivoted closed substantially flush in the outer and inner skins 38,40 respectively.
  • the deployed position is illustrated in Figure 3 at which the outer doors 54,56 are pivoted open and extend radially outwardly in part from the outer skin 38, with the inner door 58 being pivoted open and extending radially inwardly in most part from the inner skin 40.
  • the outer and inner doors are interconnected by the drive link 60 in an accordion or bifold manner in which the doors collapse or fold together in the stowed position illustrated in Figure 2, and swing open with opposite inclinations in the deployed position illustrated in Figure 3.
  • a pair of the outer louver doors 54,56 are an-anged in axial series in the common flow tunnel 52 in axial and circumferential alignment atop the common blocker door 58 disposed therebelow.
  • An elongate unison link 64 pivotally joins together the gang of louver doors 54 so that they may open and close simultaneously in the manner of commonly known louver windows.
  • louver doors 54,56 and blocker door 58 may be suitably mounted to the fan nacelle in any convenient manner for effecting the improved deployment thereof as described above.
  • a pair of circumferentially spaced apart cantilevers 66 have corresponding proximal ends which are suitably fixedly mounted to the nacelle in the common compartment 50.
  • the cantilevers are preferably thin beams circumferentially and thick radially to provide sufficient strength for supporting the louver doors therefrom while minimizing obstruction of the airflow during thrust reverse operation.
  • the two cantilevers 66 define with the two deployed louver doors a grate like those typically found in fixed cascade vanes, but using the movable louver doors.
  • the aft louver door 56 is suitably pivotally joined to the distal ends of the two cantilevers, with the forward louver door 54 being pivotally joined at an intermediate location on the cantilevers forward of the aft distal end thereof.
  • the thin cantilevers support the louver doors under tension against the aerodynamic pressure loads exerted on the louver doors when deployed.
  • a pair of the unison links 64 are correspondingly mounted to the louver doors 54,56 axially along respective ones of the two cantilevers 66.
  • two corresponding drive links 60 extend from the aft ends of the unison links to the forward ends of the blocker doors.
  • louver doors 54,56 and the cooperating blocker door 58 permits the introduction of a relatively simple mechanism for self-locking or self-latching the cooperating doors in their stowed positions without the need for external power or control dedicated thereto.
  • This self-locking capability is effected by introducing one or more substantially identical toggle links 68 suitably pivotally joined between one or both louver doors 54,56 and the supporting nacelle 16 as illustrated in Figures 2 and 3.
  • the forward toggle link 68 For the forward toggle link 68, its outer distal end is laterally offset axially aft in the outboard direction of its vertical toggle line in the stowed position of the forward louver door 54, and oppositely laterally offset axially forwardly in the inboard direction of its toggle line in the deployed position of the forward louver door.
  • the toggle link 68 toggles between the opposite sides of the forward toggle line relative to the corresponding hinge axis of the forward louver door 54.
  • the left distal end thereof is laterally offset radially outwardly in the outboard direction of its horizontal toggle line in the stowed position of the door, and oppositely laterally offset radially inwardly of its toggle line in the deployed position of the aft louver door.
  • the aft toggle link 68 therefore similarly toggles between the opposite sides of the aft toggle line between the stowed and deployed positions of the aft louver door 56.
  • the forward and aft toggle links 68 are preferably telescopic and vary in length as they are toggled during operation.
  • the toggle links are suitably configured for requiring increasing compression force as their lengths decrease between their opposite proximal and distal ends, by using an internal compression spring for example.
  • the two louver doors 54,56 cooperate with the inner blocker door 58 using the corresponding drive links 60 therebetween.
  • Each of the two louver doors 54,56 as disclosed above may be independently locked or latched using the corresponding toggle link 68 as the louver and blocker doors are stowed.
  • the toggle links described above are passive devices for latching closed the louver doors upon stowing thereof, an additional level or redundancy to latch closed the louver doors is required for meeting government certification requirements.
  • each of the forward louver doors 54 includes a latch pin 70 fixedly mounted to the middle of the forward distal end of the door and extending radially inwardly.
  • the pin 1 itself is oriented in the circumferential direction, and is suitably mounted between two side plates in an 2 integrated bracket mounted to the underside of the leading edge lip of the forward louver door.
  • Figure 2 illustrates the forward louver door latched closed, with Figure 3 illustrating unlatching 4 thereof for thrust reverser operation.
  • Each of the latch pins 70 cooperates with a complementary rotary latch 5 hook 72 pivotally mounted to the nacelle.
  • the latch hook has a latched or closed rotary position as illustrated in Figure 2 which engages the 7 latch pin 70 therein for locking or latching closed the forward louver door 54 in the outer skin.
  • the latch 8 hook also has an opposite open or unlatched rotary position as illustrated in Figure 3 which permits the latch 9 pin 70 to disengage therefrom as the forward reverser door 54 is deployed radially outwardly.
  • An actuator-driven rotary cam may be mounted on the front side of the rotary latch to lock it closed
  • the spider actuation system 62 introduced above is specifically configured for simultaneously
  • each of the forward doors 54 includes a pivot axis or joint 74 disposed at an
  • Figure 4 illustrates in more particularity two of the pivot joints 74 defining the common pivot axis
  • Each forward door 54 preferably also includes a drive bracket or clevis 76 mounted between the two
  • pivot joints 74 which is fixedly mounted to the inner surface of the door slightly aft of the pivot axis.
  • 27 system includes an arcuate peripheral bar or yoke 78 disposed coaxially around the centerline axis 30 of the
  • each yoke 29 are provided in both halves of the nacelle, with each yoke extending suitably less than the 180 degree
  • a single or common linear actuator 80 is suitably mounted tangentially to the yoke 78 for rotary
  • the actuator may have any
  • 33 conventional configuration, and may be electrical, pneumatic, or hydraulic, with an extendable output rod.
  • a plurality of drive or spider rods 82 are spaced circumferentially apart around the common yoke 78
  • Each rod has a proximal
  • the drive fitting 84 of the spider rod 82 is joined to the drive clevis 76 on each forward door using a short idler link 86 which accommodates differential radial movement between the rod 82 and the drive clevis 76 as the forward door 54 is pivoted between its deployed and stowed positions.
  • the full set of spider rods 82 three for example as illustrated in Figure 5, extend axially or parallel to centerline axis 30 of the nacelle and extend axially aft from the common yoke 78 for simultaneously pivoting the corresponding forward reverser doors 54 as the common actuator 80 rotates the yoke circumferentially.
  • the common yoke 78 provides synchronous axial deployment of the spider rods 82 for simultaneously pivoting the set of forward reverser doors in each C-duct.
  • the actuation system 62 illustrated in Figure 5 is suitably supported inside the nacelle 16 from a common radial frame 88 which is itself fixedly mounted in the nacelle.
  • a plurality of local frames or stanchions 90 are fixedly mounted to the radial frame 88 at respective ones of the spider rods 82.
  • the stanchions support the yoke 78 and permit circumferential rotary movement thereof, while also supporting the actuator drive rods 82 and permitting axial translation thereof.
  • each of the spider rods 82 illustrated in Figures 5 and 6 is slidably mounted in tubular housing 92, which housing itself is fixedly joined to the corresponding stanchion 90 axially perpendicularly aft from the common yoke 78.
  • the yoke 78 includes an inclined circumferential drive slot 94 at each of the spider rods 82, and each of the spider rods includes a complementary drive roller 96 at the proximal end thereof disposed in a respective one of the drive slots.
  • the drive slots 94 engage the drive rollers 96 for driving each rod in axial translation to pivot the attached reverser doors.
  • the yoke 78 may have any suitable configuration, such as a hollow tubular component, and preferably includes local rectangular spider channels 78a slidingly supported in each of the stanchions 90 for receiving corresponding ones of the spider rods.
  • each channel 78a has radially inner and outer arcuate plates joined together at a radially extending base at the forward end thereof forming a generally U-shaped cross section, being open at the aft end thereof.
  • Each plate of the channel includes one of the drive slots 94 therein which receives a corresponding drive roller 96 joined to the proximal end of the spider rod 82.
  • the drive slots 94 engage the drive rollers 96 for reducing friction therewith and carrying axial force through the several spider rods 82 to pivot the reverser doors.
  • the channels 78a are mounted in the stanchions 90 for low friction rotary movement by a plurality of guide rollers 98.
  • Figures 7-9 illustrate two sets of four guide rollers 98 mounted on opposite axial sides of the channel 78a to simultaneously support the inner and outer plates thereof along their forward and aft ends.
  • Each of the guide rollers 98 includes a suitable lip to trap and suspend radially the channel 78a on each stanchion.
  • the common yoke 78 is mounted at each of the circumferentially spaced apart stanchions by the guide rollers 98 mounted therein for trapping each channel 78 axially and radially and permitting low friction circumferential rotary movement thereof.
  • the guide rollers 98 illustrated in Figure 7 are mounted in radial pairs with a common fastener 2 extending therethrough.
  • the fasteners are fixedly joined to inner and outer supporting plates of the stanchion.
  • the two drive rollers 96 are mounted at the proximal end of the spider rod 82 by another fastener extending 4 radially therethrough.
  • the head and nut ends of this fastener may extend radially through axial extending 5 cutout slots in the two stanchion plates for permitting unrestrained axial movement of the spider rod 82 as the 6 yoke channel 78a rotates circumferentially inside each stanchion.
  • the drive slots 94 are disposed in the top and bottom channel plates for 8 receiving the corresponding drive rollers 96 therein.
  • the corresponding spider rods 82 then extend axially aft 9 and outwardly through the open ends of the channels toward the respective reverser doors.
  • the drive slots 94 extend circumferentially along the channel plates
  • each drive roller 96 is slightly less than the width of the drive slot 94 so that the forward side of
  • Figures 5 and 7 illustrate tangential extension of the output rod of the common drive actuator 80, which in
  • Figure 6 illustrates retraction of the output rod of the common actuator 80 which in turn retracts the
  • the inclination angle A of the drive slots 94 is preferably shallow and less than or equal to 45
  • the axial stroke of the rods 82 may be minimized for reducing the size of the linkages which pivot the
  • the inclination angle A of the drive slots 94 is preferably less than 45 degrees for
  • the cam action of the inclined drive slots 94 provide a simple and effective 1 mechanical force leverage which offsets stroke length. Force amplification may be obtained at the expense of 2 increased circumferential stroke, with the decreased axial stroke of the spider rods 82 being used to advantage 3 for increasing the speed of deployment and retraction of the reverser doors. 4 As indicated above, the inclination angle of the drive slots 94 may be less than or equal to 45 5 degrees.
  • the axial stroke B of the spider rods 82 illustrated in Figure 5 is proportional to the circumferential 6 stroke C of the yoke 78 by the tangent of the inclination angle A.
  • the inclination angle A of the drive slots 94 is about 10 degrees for
  • the axial stroke B required to fully deploy the forward reverser doors may be
  • the actuator 80 may be relatively small, with relatively small stroke itself, and with
  • each of the drive slots 94 preferably includes detent notches 94a at opposite
  • the notches 94a are disposed perpendicular to the rods 82 and prevent relative movement between the circumferential yoke and the axial rods 82 when the rollers 96 are disposed therein. In this way, when the drive rollers 96 are located at either end of the drive slot 94 in the respective detent notch 94a the rods 82 are locked in axial position either fully extended or fully retracted.
  • the drive rollers 96 are trapped in the aft detent notches 94a which in turn adds redundancy to the locking mechanisms for stowing closed the thrust reverser doors.
  • the thrust reverser doors are locked open, and the various loads acting on the doors are carried in part axially through the common yoke 78 into the nacelle frame.
  • the common yoke 78 extends in circumferential length suitably less than the 180 degree extent of the C-duct nacelle half to commonly drive the three sets of thrust reverser doors in unison. Accordingly, the common yoke 78 includes three of the spider channels 78a distributed at opposite circumferential ends of the yoke and in the middle thereof.
  • the single drive actuator 80 is fixedly mounted to the radial frame 88 and includes an output rod extending tangentially to the yoke and joined to a supporting bracket 100 fixedly mounted on the end channel 78a located at the proximal end of the yoke.
  • the opposite, distal end of the common yoke 78 extends freely from the third stanchion 90 which supports this end.
  • the spider mechanism 62 illustrated in Figure 5 is reproduced in mirror image on the opposite C-duct of the fan nacelle for similarly driving in unison the three sets of thrust reverser doors in that half of the fan nacelle.
  • the spider actuation mechanism disclosed above enjoys many advantages in deploying and retracting the bifold door thrust reverser.
  • the close mounting of the pivot joint 74 and drive bracket 76 for the forward louver doors permits large angular deployment thereof with minimal axial stroke of the spider rods 82, which may be as little as about 50 mm.
  • the multiple sets of reverser doors may be accurately driven in unison using the axial spider rods driven by the common circumferential yoke using a single actuator.
  • the drive slot interconnection between the yoke and spider rods enjoys substantial mechanical leverage in which small stroke and large force may be obtained in each of the spider rods with correspondingly large circumferential stroke and small force in the yoke and single drive actuator.
  • the circumferential orientation of the yoke permits relatively large circumferential stroke which is converted to relatively small axial stroke in each of the spider rods.
  • this mechanical advantage also permits the use of a relatively small actuator to develop suitably larger force as required to drive the several spider rods in unison.
  • Operation of the several gangs of thrust reverser doors is inherently synchronized using the common yoke and spider rods, with a single small actuator instead of using individual large actuators for each of the reverser door sets.
  • Pivoting of the reverser door sets has substantially improved accuracy since the small axial stroke required therefor is obtained by correspondingly larger circumferential stroke of the common yoke. Since actuators are inherently heavy and expensive for large force requirements, a substantial reduction in weight and cost may be obtained by using the single small actuator for driving the common yoke, which in turn drives the multiple spider rods joined thereto.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Wind Motors (AREA)
  • Agricultural Machines (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)

Abstract

Inverseur de poussée (36) comprenant des portes d'inversion (54) espacées sur la circonférence d'une nacelle (16). Une bride incurvée (78) est placée sur le même axe autour de la nacelle. Un organe de commande (80) est monté tangentiellement par rapport à la bride (78) afin de l'entraîner en rotation. Des tiges de commande (82) relient les portes (54) à la bride (78) afin de déployer les portes (54) simultanément à la rotation de la bride (78).
EP04821621A 2003-10-02 2004-10-01 Inverseur de poussee mis en service par une suspension en forme d'araignee Withdrawn EP1733134A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US50850403P 2003-10-02 2003-10-02
PCT/US2004/032370 WO2005094227A2 (fr) 2003-10-02 2004-10-01 Inverseur de poussee mis en service par une suspension en forme d'araignee

Publications (2)

Publication Number Publication Date
EP1733134A2 true EP1733134A2 (fr) 2006-12-20
EP1733134A4 EP1733134A4 (fr) 2010-08-11

Family

ID=35064217

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04821621A Withdrawn EP1733134A4 (fr) 2003-10-02 2004-10-01 Inverseur de poussee mis en service par une suspension en forme d'araignee

Country Status (5)

Country Link
US (1) US7264203B2 (fr)
EP (1) EP1733134A4 (fr)
BR (1) BRPI0414914A (fr)
CA (1) CA2536739A1 (fr)
WO (1) WO2005094227A2 (fr)

Families Citing this family (59)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7264203B2 (en) * 2003-10-02 2007-09-04 The Nordam Group, Inc. Spider actuated thrust reverser
GB0606823D0 (en) * 2006-04-05 2006-05-17 Rolls Royce Plc Adjustment assembly
US7721551B2 (en) 2006-06-29 2010-05-25 United Technologies Corporation Fan variable area nozzle for a gas turbine engine fan nacelle
US8015797B2 (en) 2006-09-21 2011-09-13 Jean-Pierre Lair Thrust reverser nozzle for a turbofan gas turbine engine
WO2008045069A1 (fr) * 2006-10-12 2008-04-17 United Technologies Corporation Tuyère à section variable à soufflante avec actionneur électromécanique
EP1916405B1 (fr) * 2006-10-17 2018-12-26 United Technologies Corporation Tuyère à section variable de contrôle du vecteur de poussée pour nacelle de soufflante de turboréacteur
FR2915526B1 (fr) * 2007-04-24 2009-05-29 Aircelle Sa Dispositif de variation de section de tuyere secondaire associe a un inverseur a portes a dispositif de lissage de veine.
US9759087B2 (en) 2007-08-08 2017-09-12 Rohr, Inc. Translating variable area fan nozzle providing an upstream bypass flow exit
EP2578864B1 (fr) * 2007-08-08 2014-09-24 Rohr, Inc. Tuyère de soufflante à surface variable avec écoulement de dérivation
FR2922958B1 (fr) * 2007-10-25 2009-11-20 Aircelle Sa Inverseur de poussee a grilles
US8052086B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser door
US8172175B2 (en) 2007-11-16 2012-05-08 The Nordam Group, Inc. Pivoting door thrust reverser for a turbofan gas turbine engine
US7735778B2 (en) * 2007-11-16 2010-06-15 Pratt & Whitney Canada Corp. Pivoting fairings for a thrust reverser
US8091827B2 (en) 2007-11-16 2012-01-10 The Nordam Group, Inc. Thrust reverser door
US8052085B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
US8051639B2 (en) 2007-11-16 2011-11-08 The Nordam Group, Inc. Thrust reverser
US8127530B2 (en) 2008-06-19 2012-03-06 The Nordam Group, Inc. Thrust reverser for a turbofan gas turbine engine
FR2933143B1 (fr) * 2008-06-26 2011-06-10 Airbus France Nacelle pour aeronef comportant des moyens inverseurs de poussee et aeronef comportant au moins une telle nacelle
FR2954409A1 (fr) * 2009-12-18 2011-06-24 Aircelle 7298 Dispositif d'inverseur de poussee
US8869507B2 (en) * 2010-01-13 2014-10-28 United Technologies Corporation Translatable cascade thrust reverser
US20110296812A1 (en) * 2010-06-08 2011-12-08 Honeywell International Inc. Thrust reverser actuation system architecture
FR2966883B1 (fr) * 2010-11-03 2012-11-02 Aircelle Sa Dispositif d'inversion de poussee sans bielle dans la veine
US8713911B2 (en) 2010-12-15 2014-05-06 Woodward Hrt, Inc. System and method for operating a thrust reverser for a turbofan propulsion system
US20130042630A1 (en) * 2011-08-19 2013-02-21 United Technologies Corporation Gas turbine engine accessory mount
FR2982323B1 (fr) * 2011-11-07 2013-11-15 Aircelle Sa Dispositif d'inversion de poussee
FR2985782B1 (fr) * 2012-01-17 2015-07-24 Aircelle Sa Inverseur de poussee a portes jumelles
US9086035B2 (en) * 2012-01-20 2015-07-21 Hamilton Sundstrand Corporation Integrated thrust reverser actuator and variable area fan nozzle actuator
US9091230B2 (en) * 2012-05-16 2015-07-28 The Boeing Company Linked ring petal actuation for variable area fan nozzle
US9068532B2 (en) * 2012-07-24 2015-06-30 Rohr, Inc. Translating sleeve thrust reverser with movable cascade
FR2993932B1 (fr) * 2012-07-27 2015-09-25 Aircelle Sa Dispositif d'entrainement de volets notamment pour tuyere adaptative
US20140225388A1 (en) * 2013-02-11 2014-08-14 United Technologies Corporation Latch release mechanism
US9694912B2 (en) 2013-02-22 2017-07-04 United Technologies Corporation ATR guide pins for sliding nacelle
US9581108B2 (en) 2013-02-22 2017-02-28 United Technologies Corporation Pivot thrust reverser with multi-point actuation
US9435293B2 (en) 2013-02-22 2016-09-06 United Technologies Corporation Full ring sliding nacelle with thrust reverser
US10060292B2 (en) 2013-03-14 2018-08-28 United Technologies Corporation Castellated latch mechanism for a gas turbine engine
US9650992B2 (en) * 2013-10-17 2017-05-16 Rohr, Inc. Core cowl thrust reverser system and apparatus
US9765729B2 (en) * 2013-10-17 2017-09-19 Rohr, Inc. Thrust reverser fan ramp with blocker door pocket
US9938929B2 (en) 2014-03-21 2018-04-10 Rohr, Inc. Thrust reverser for a turbofan engine
US10077739B2 (en) * 2014-04-24 2018-09-18 Rohr, Inc. Dual actuation system for cascade and thrust reverser panel for an integral cascade variable area fan nozzle
US10487690B2 (en) * 2014-08-18 2019-11-26 Rohr, Inc. Actively controlled cooling air exhaust door on an aircraft engine nacelle
US9945324B2 (en) 2014-11-06 2018-04-17 Rohr, Inc. Sleeve linkage for thrust reverser
US10309343B2 (en) 2014-11-06 2019-06-04 Rohr, Inc. Split sleeve hidden door thrust reverser
US9784214B2 (en) * 2014-11-06 2017-10-10 Rohr, Inc. Thrust reverser with hidden linkage blocker doors
US10208708B2 (en) 2015-01-29 2019-02-19 Rohr, Inc. Translating cascade hidden blocker door thrust reverser
US10473057B2 (en) 2015-12-14 2019-11-12 Rohr, Inc. Thrust reverser system with translating elements
US10533519B2 (en) * 2016-01-13 2020-01-14 Rohr, Inc. Translating cascade hidden blocker door thrust reverser
US10563615B2 (en) * 2016-05-09 2020-02-18 Mra Systems, Llc Gas turbine engine with thrust reverser assembly and method of operating
US10655564B2 (en) 2016-05-13 2020-05-19 Rohr, Inc. Thrust reverser system with hidden blocker doors
US9976696B2 (en) 2016-06-21 2018-05-22 Rohr, Inc. Linear actuator with multi-degree of freedom mounting structure
FR3054266B1 (fr) * 2016-07-25 2018-08-31 Safran Nacelles Systeme d’actionnement d’un panneau de nacelle de turboreacteur
US10724475B2 (en) * 2016-09-27 2020-07-28 The Boeing Company Dual turn thrust reverser cascade systems and methods
US10618664B2 (en) * 2017-06-16 2020-04-14 Rohr, Inc. Self-latching nacelle
US10801339B2 (en) 2017-07-11 2020-10-13 General Electric Company Aircraft gas turbine engine variable fan blade mechanism
EP3489547B1 (fr) 2017-11-27 2022-05-04 Rohr, Inc. Inverseur de poussée avec dispositif de commande de mouvements
CN109441661A (zh) * 2018-12-21 2019-03-08 湖北鸿翼航空科技有限公司 一种涡轮风扇发动机短舱外涵道反推力装置
GB2588653A (en) * 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588652A (en) * 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588651A (en) 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
US11719190B2 (en) 2021-10-05 2023-08-08 Rohr, Inc. Thrust reverser system with hidden turning door

Family Cites Families (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB913699A (fr) 1959-12-18
US3503211A (en) 1968-04-10 1970-03-31 Rohr Corp Thrust reverser
US3614037A (en) 1969-09-22 1971-10-19 Boeing Co Aircraft combination thrust reverser and sound suppressor and a particular full range balanced thrust reverser
US3779010A (en) 1972-08-17 1973-12-18 Gen Electric Combined thrust reversing and throat varying mechanism for a gas turbine engine
US3829020A (en) * 1973-06-13 1974-08-13 Boeing Co Translating sleeve variable area nozzle and thrust reverser
US4030290A (en) * 1974-11-06 1977-06-21 The Boeing Company Jet engine thrust reverser
US4147029A (en) 1976-01-02 1979-04-03 General Electric Company Long duct mixed flow gas turbine engine
FR2622929A1 (fr) 1987-11-05 1989-05-12 Hispano Suiza Sa Inverseur de poussee de turboreacteur a grilles,a section variable d'ejection
FR2727468B1 (fr) 1994-11-30 1996-12-27 Hispano Suiza Sa Inverseur de poussee de turboreacteur a obstacles aval
US5655360A (en) 1995-05-31 1997-08-12 General Electric Company Thrust reverser with variable nozzle
FR2741910B1 (fr) 1995-11-30 1998-01-02 Hispano Suiza Sa Inverseur de poussee de turboreacteur a portes a panneau arriere articule
US5826823A (en) 1996-02-07 1998-10-27 Rohr, Inc. Actuator and safety lock system for pivoting door thrust reverser for aircraft jet engine
FR2745036B1 (fr) * 1996-02-15 1998-04-03 Hispano Suiza Sa Inverseur de poussee de turboreacteur a portes associees a un panneau amont
US5908159A (en) * 1997-02-24 1999-06-01 The Boeing Company Aircraft chute ejector nozzle
GB9825651D0 (en) * 1998-11-23 1999-01-13 Lucas Ind Plc Actuator
US6487846B1 (en) * 2001-09-07 2002-12-03 Honeywell International, Inc. Thrust reverser actuator including an integrated locking mechanism
FR2830051B1 (fr) 2001-09-27 2003-11-07 Hurel Hispano Le Havre Systeme de verrouillage sur un inverseur de poussee a grilles
US6568172B2 (en) 2001-09-27 2003-05-27 The Nordam Group, Inc. Converging nozzle thrust reverser
US6598386B2 (en) * 2001-10-16 2003-07-29 Honeywell International, Inc. Jet engine thrust reverser system having torque limited synchronization
US6845607B2 (en) * 2002-01-09 2005-01-25 The Nordam Group, Inc. Variable area plug nozzle
US6666307B1 (en) * 2002-08-05 2003-12-23 Honeywell International, Inc. Thrust reverser system with a pass-through torque activated brake
CA2501496A1 (fr) 2002-10-11 2004-06-03 The Nordam Group, Inc. Inverseur de poussee a volet double pliant
US6968675B2 (en) * 2002-10-29 2005-11-29 Rohr, Inc. Cascadeless fan thrust reverser with plume control
US6845946B2 (en) * 2003-02-21 2005-01-25 The Nordam Group, Inc. Self stowing thrust reverser
US6976352B2 (en) * 2003-03-22 2005-12-20 The Nordam Group, Inc. Toggle interlocked thrust reverser
US20050001095A1 (en) * 2003-05-05 2005-01-06 Christensen Donald J. Self-aligning thrust reverser system lock assembly
US6966175B2 (en) * 2003-05-09 2005-11-22 The Nordam Group, Inc. Rotary adjustable exhaust nozzle
US6974107B2 (en) * 2003-06-18 2005-12-13 Honeywell International, Inc. Thrust reverser system actuator having an integral torque limiter
US7127880B2 (en) * 2003-08-29 2006-10-31 The Nordam Group, Inc. Induction coupled variable nozzle
US7093793B2 (en) * 2003-08-29 2006-08-22 The Nordam Group, Inc. Variable cam exhaust nozzle
US7146796B2 (en) * 2003-09-05 2006-12-12 The Nordam Group, Inc. Nested latch thrust reverser
US7264203B2 (en) * 2003-10-02 2007-09-04 The Nordam Group, Inc. Spider actuated thrust reverser
US7278258B2 (en) * 2004-11-12 2007-10-09 Honeywell International, Inc. Floating flexible firewall seal
US7409820B2 (en) * 2004-11-16 2008-08-12 Honeywell International Inc. Electrical thrust reverser tertiary lock system including a voltage limiting circuit

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
No further relevant documents disclosed *
See also references of WO2005094227A2 *

Also Published As

Publication number Publication date
US20050151012A1 (en) 2005-07-14
US7264203B2 (en) 2007-09-04
EP1733134A4 (fr) 2010-08-11
CA2536739A1 (fr) 2005-10-13
WO2005094227A2 (fr) 2005-10-13
WO2005094227A3 (fr) 2007-01-04
BRPI0414914A (pt) 2006-12-26

Similar Documents

Publication Publication Date Title
US7264203B2 (en) Spider actuated thrust reverser
US7146796B2 (en) Nested latch thrust reverser
US6976352B2 (en) Toggle interlocked thrust reverser
US6895742B2 (en) Bifold door thrust reverser
CA2517563C (fr) Tuyere d'echappement rotative et reglable
US7093793B2 (en) Variable cam exhaust nozzle
US6845946B2 (en) Self stowing thrust reverser
US11927150B2 (en) Drive system for translating structure
US20230272760A1 (en) Mixed flow exhaust thrust reverser with area control nozzle systems and methods
US10641208B2 (en) Translating nozzle for mixed flow turbofan engine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20060424

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL HR LT LV MK

PUAK Availability of information related to the publication of the international search report

Free format text: ORIGINAL CODE: 0009015

RIC1 Information provided on ipc code assigned before grant

Ipc: F16H 57/02 20060101ALI20090917BHEP

Ipc: F02K 1/54 20060101AFI20090917BHEP

A4 Supplementary search report drawn up and despatched

Effective date: 20100709

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20110206